| タイトル | Airfoil Dynamic Stall and Rotorcraft Maneuverability |
| 本文（外部サイト） | http://hdl.handle.net/2060/20010038509 |
| 著者（英） | Bousman, William G. |
| 著者所属（英） | NASA Ames Research Center|Army Aviation and Missile Command |
| 発行日 | 2000-07-01 |
| 言語 | eng |
| 内容記述 | The loading of an airfoil during dynamic stall is examined in terms of the augmented lift and the associated penalties in pitching moment and drag. It is shown that once stall occurs and a leading-edge vortex is shed from the airfoil there is a unique relationship between the augmented lift, the negative pitching moment, and the increase in drag. This relationship, referred to here as the dynamic stall function, shows limited sensitivity to effects such as the airfoil section profile and Mach number, and appears to be independent of such parameters as Reynolds number, reduced frequency, and blade sweep. For single-element airfoils there is little that can be done to improve rotorcraft maneuverability except to provide good static C(l(max)) characteristics and the chord or blade number that is required to provide the necessary rotor thrust. However, multi-element airfoils or airfoils with variable geometry features can provide augmented lift in some cases that exceeds that available from a single-element airfoil. The dynamic stall function is shown to be a useful tool for the evaluation of both measured and calculated dynamic stall characteristics of single element, multi-element, and variable geometry airfoils. |
| NASA分類 | Aircraft Stability and Control |
| レポートNO | NAS 1.15:209601
AFDD/TR-00-A-008
A-00V0021
NASA/TM-2000-209601 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/226277 |
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